At high edgewise flow speeds, reversed flow causes excursions in pitching moment and blade torsion on the rotor blades of helicopters and wind turbines. Our prior work has shown that a yawed fixed wing at angle of attack in reversed flow generates a sharp-edge vortex. The sharp-edge vortex is a primary feature of the flow under the rotor blade. During operation as a rotor blade at high advance ratio in a wind tunnel, stereo PIV results show that the well-formed sharp-edge vortex at 240 degrees azimuth resembles that on a forward-swept wing. This vortex stops growing before 270 degrees and convects with the blade by 300 degrees. Static pressure computed from interpolated velocity data show the effects of vortex-induced radial pressure gradient. This explains the finding of inboard-directed radial flow at 300 degrees azimuth, overcoming centrifugal effects. Viscous stress is shown to have only a minor effect on the static pressure field computation.
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ASME/JSME/KSME 2015 Joint Fluids Engineering Conference
July 26–31, 2015
Seoul, South Korea
Conference Sponsors:
- Fluids Engineering Division
ISBN:
978-0-7918-5721-2
PROCEEDINGS PAPER
Dynamic Effects in the Reverse Flow Velocity Field Available to Purchase
Nandeesh Hiremath,
Nandeesh Hiremath
Georgia Tech, Atlanta, GA
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Vrishank Raghav,
Vrishank Raghav
Georgia Tech, Atlanta, GA
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Narayanan Komerath
Narayanan Komerath
Georgia Tech, Atlanta, GA
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Dhwanil Shukla
Georgia Tech, Atlanta, GA
Nandeesh Hiremath
Georgia Tech, Atlanta, GA
Vrishank Raghav
Georgia Tech, Atlanta, GA
Narayanan Komerath
Georgia Tech, Atlanta, GA
Paper No:
AJKFluids2015-13545, V001T13A002; 8 pages
Published Online:
November 20, 2015
Citation
Shukla, D, Hiremath, N, Raghav, V, & Komerath, N. "Dynamic Effects in the Reverse Flow Velocity Field." Proceedings of the ASME/JSME/KSME 2015 Joint Fluids Engineering Conference. Volume 1: Symposia. Seoul, South Korea. July 26–31, 2015. V001T13A002. ASME. https://doi.org/10.1115/AJKFluids2015-13545
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